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April 2nd, 2007
The USA Demonstrator FI-156
arrived in Miami on March 31st, via Air Cargo in a specially constructed container, which allowed it to require minimal disassembly. This aircraft will be going to our Titusville, FL maintenance base, where it will be reassembled, test-flown and taken to the 2007 Sun'nFun Expo in Lakeland, Florida from April 17th to 23rd. The aircraft will be on display at the Light Aircraft Section of the show
April 17 - 23, 2007
Sun 'n Fun Fly-In
Visit: www.sun-n-fun.org
Our Aircraft
FIESELER STORCH FI-156 - Construction
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Fuselage
THE CRIQUET STORCH UTILIZES A FUSELAGE KNOWN AS THE WARREN TRUSS. Jigs are used for the construction of the fuselage.
The materials used for the construction of the fuselage are aeronautical materials which assure great quality and strength to all the structural parts. These materials are:
- Tubes of steel chromium-molybdenum (SAE 4130), for the fuselage structure.
- Aluminum 2024-T3 for the lower fuselage skin, below the instruments panel, held with AN470-AD3-4 rivets.
- Aluminum 6061-T6 for the lateral wall of the fuselage section of the instrument panel, held with rivets AN470-AD3-4
- TIG Welding “Tungsten Inert Gas"
Wing
The wings have fixed slats in the leading edge to improve lift and maneuverability at low speeds.
RIBS: There are total of 19 in the wing, made of Aluminum Sheet 2024 - T3 with its respective lightening holes at the attack and trailing edges: they are made with 2024-T3 Aluminum Sheets. The main spar is C shaped and made of 2024-T3 Aluminum.
The central part of the plane, in the front and rear spars, has two support attachments, made out of 2024 T3 Aluminum sheeting. The flap plates and the ailerons are riveted to the ribs of the trailing edge with AN470 AD-5 rivets.
Landing Gear
The Criquet Storch landing gear type is called skate. Its construction followed the original design, but analyzed structurally according to the operational conditions and maximum weight of our aircraft. It consists of two main gear strains and a couple of v profiled tubes that support the lateral, drag and impact loads. The main wheels transmit the load directly to the shocks and the attach points in the fuselage and a main structural station.
Tubes of chromium-molybdenum (SAE 4130) steel of different sizes and thicknesses are used, according to the stress requirements in the various landing gear parts.
The shock absorber system consists of steel springs similar to the original design. It consists of a cylinder and a piston, with two springs; one the compression spring and the other the dampener.