TCDS A7NM

Page No. 1 2 Rev. No. - - DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A7NM RYSON ST-100 TYPE CERTIFICATE DATA SHEET NO. A7NM This data sheet which is a part of Type Certificate No. A7NM prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations. Type Certificate Holder: Ryson Aviation Corporation 548 San Fernando Street San Diego, California 92106 Model ST-100 (Airplane Normal Category, Airplane Utility Category, and Airplane Acrobatic Category), approved July 29, 1983. Engine Teledyne Continental Motors O-200-A Fuel 80/87 octane (min. grade aviation gasoline) Engine limits Sea level static: takeoff 2750 RPM (100 hp) maximum continuous 2750 RPM (100 hp) Propeller and (a) Hoffmann HO-V62-R/107Y propeller limits (b) Pitch Control Mech. No. VP20-588 (c) Spacer No. VP20-580 (d) Spinner - Ryson P/N 40-011-33 (e) Pitch settings measured at 25 in: full diameter of 67 in Low 16.0° + 1.0° High 20.5° + 1.0° minimum diameter of 64 in Low 17.5° + 1.0° High 22.0° + 1.0° Airspeed limits Reduce Vno 1 knot per 1000 ft of altitude above sea level (CAS) All airplane categories Maneuvering - Va 108 knots (124 mph) Maximum structural cruising - Vno 122 knots (140 mph) Never exceed - Vne 140 knots (178 mph) Flaps extended - Vfe 108 knots (124 mph) C.G. range All weights and categories + 51.74 to + 56.54 in aft of datum (28% MAC to 38% MAC Leveling means Upper longeron Maximum weight TAKEOFF LANDING Airplane normal 1750 lb 1702 lb Airplane utiltiy 1750 lb 1702 lb Airplane acrobatic 1650 lb 1650 lb No. of seats Maximum 2 Front seat at F.S. +89.0 Rear seat at F.S. +123.0 A7NM 2 Minimum Crew One Datum Front face of engine firewall (F.S. +50.0) Maximum baggage 20 lb at F.S. +144.0 Fuel capacity Two wing tanks, total 32 US gal (30 US gal usable) at F.S. +98.0 Oil capacity 6 US quarts (Max.) at F.S. +39.0 Control surface movements Position of flap/aileron Differential aileron available -12 degrees (up) +7 degrees (dwn) to -27 degrees (up) 0 degrees (neutral) +18 degrees (dwn) to -27 degrees (up) +8 degrees (dwn) +18 degrees (dwn) to -20 degrees (up) * +60 degrees (dwn) +18 degrees (dwn) to -20 degrees (up) *Note: For this position the flap only is down 60 degrees. The aileron is limited to 8 degrees down. All movements within + 1° Serial Nos. eligible S/N 001 and above Certification basis The Model ST-100 is certificated as an airplane. It meets the applicable requirements of: 1. Part 23 of the Federal Aviation Regulations effective February 1, 1965, as amended through Amendment 23-20 with the exception of FAR 23.1323 (Exemption No. 3551 dated June 28, 1982). 2. Part 36 of the Federal Aviation Regulations effective December 1, 1969, as amended through Amendment 36-12. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. NOTE 1. Current weight and balance data together with list of equipment included in the certificated empty weight, and loading instructions when necessary, must be provided for each aircraft at the time of original certification. NOTE 2. Operational limitations. The airplane is approved for day VFR only. FAR Part 91 establishes the minimum required instrumentation and equipment for this operation. Flight into known icing conditions is prohibited. NOTE 3. Ryson Aviation Corporation FAA Approved Airplane Flight Manual and FAA Approved Glider (Powered) Flight Manual, Report No. 100, incorporate a list of required placards, current weight and balance data, and equipment list. NOTE 4. The ST-100 is eligible for an Airworthiness Certificate as an airplane under this data sheet, or a self-launching (powered) glider under Data Sheet G1NM, or as an airplane/self-launching (powered) glider. .....END....