AOSS

Among the many new aspects of the AOSS the one that almost outshines the AOSS' performance is the
ability of the shock strut to be ground adjustable by the pilot in the instance of heavy loading of the
aircraft. This adjustability also allows for compensation landing gear fittings that may not be installed as
accurately as one would desire.

The AOS System currently approved is designed and engineered to be installed on the Piper PA-18,
serial nos. 18-3771, 18-3781 and up; PA-18A, serial nos. 18-3771, 18-3786 and up; PA-18-135 through
PA-18-150; and Piper PA-12 and PA-14 (when modified to PA-18 landing gear in accordance with FAA
approved data). All seaplane versions of the aforementioned aircraft are also approved. At a later date,
other models of aircraft will be added, including the Husky A-1 and A-1B, the Arctic Tern and the Aeronca
Sedan. The system is approved for installation on aircraft that incorporate the new 2,000 pound gross
weight increase STC with standard length and 3" extended landing gear. Approval on the 6" extended
landing gear is not planned.

Extensive testing to date has yielded a product that exceeds our initial expectations. Dampening and
suspension characteristics are excellent. The cold-drop testing (-20º Fahrenheit) yielded a final product
that has virtually no rebound without sacrificing the suspension, active and reactive function.

The final test is the "Reserve Energy" test. This test requires the drop height to be 1.44 times the "limit
load" drop height. In this case, the height was just short of 18". The drop-test weight was calculated for a
gross weight of 2,070 lbs. (1954 PA-18A, AG Sprayer)

During the final phase of testing, the "landing" of the AOSS installed on the drop-test fixture and
associated PA-18 airframe parts and landing gear was so soft that everyone was literally stunned. The G-
force accelerations are not required to be taken into account during the "reserve energy" drop. It should
be noted that during the reserve energy drop, the rule is, it can bend, but it can't break. The AOSS did
neither. The AOSS recorded as maximum acceleration of only 4.7 g's. This is an incredibly low number
for this type of drop when forces of up to 5.2 to 5.4 g's were expected.

The first production run is expected to be available within the next ten to twelve weeks. This first run is
limited to 150 pair - if you are interested, place your order immediately. A 25% deposit will hold your
order.

With the cost of the AOSS at $2,200.00 per pair, no doubt a serious investment in your aircraft, keep in
mind there is no annual or biennial expense for changing of bungee cords/shock rings, and no downtime
to do the change. You buy AOSS once. Maintenance is reduced to a periodic change of an $8.00 seal.

Patent No. 6609682 was issued August 26, 2003.

Visit www.aoss.net for updated information on the AOS System

:: UPDATE :: The latest on the AOSS: IN STOCK AND FOR SALE NOW!!

May 5, 2004, 9:30 PM the AOSS completed the final drop-test with FAA
ACO Engineering standing by. Seven years after the idea was born, and after
three and a half years of testing, modifying, retesting, remodifying, and more
testing, the AOS System is finally available.

The AOS system utilizes a solid, deformable polymer as a suspension and
shock absorbing medium. Under normal operating conditions, you won't
notice much difference; however, this new design shock absorber and
suspension system in one puts and end to the "slingshot" effect in the
rebound from hard landings, caused by the old design rubber shock rings /
bungee cords. The body is fabricated from 3" 4130N drawn tubing,
electroless nickel plated and zinc coated. The shock strut and other
associated tubing and the attach fitting are fabricated from titanium. This
heavy duty design adds strength in all aspects of installation, operation and
adverse loading conditions. (Titanium is 44% lighter than steel and 20%
stronger.)