TCDS A16SO

Page No. 1 2 Rev. No. 2 2 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A16SO Revision 2 Falcon F-1 April 2, 1996 TYPE CERTIFICATE DATA SHEET No. A16SO This data sheet, which is a part of Type Certificate No. A16SO, 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 Elzie Wright, Jr. Route 1, Box 467 Jamestown, TN 38556 Model F-1, 2 POLB (Normal Category), Approved May 21, 1975 Engine Lycoming O-320-A2B with Marvel Schebler Carburetor MA4SPA/10-5135 Fuel 80/87 minimum grade aviation gasoline Engine limits 150 HP @ 2700 RPM for all operations Propeller and McCauley, fixed-pitch, 1A175/GM8042, Diameter 80 in. max., propeller limits 78 in. min. No additional cutoff permitted Static RPM 2450 RPM max. 2350 RPM min. No additional tolerance permitted Airspeed limits Vne (Never exceed) 120 MPH (104 KT.) (CAS) Va (Maneuvering) 106 MPH ( 92 KT.) Vno (Maximum structural cruising) 106 MPH ( 92 KT.) C.G. range (+23.6 to +27.0) at 1900 pounds (+23.6) at 1900 pounds or less (+27.0) at 1900 pounds or less Straight line variation between points given. Datum Forward face of firewall Leveling means Upper left longeron at forward cockpit Maximum weight 1900 pounds Number of seats Two (one @ +29.0, one @ +62.0) Maximum baggage 25 pounds @ +83.0 Fuel capacity 28.4 U.S. gallons @ +23.0) Usable 26.2 U.S. gallons. See Note 1 for unusable fuel. A16SO Page 2 Oil capacity 8 qts. @ -36.0. 6 qts. usable. Control surface movements Ailerons Upper: 9° ± 2° Up 19° ± 2° Down Lower: 9° ± 2° Up 14° ± 2° Down Elevator 32° ± 2° Up 30° ± 2° Down Elevator tab 12° ± 2° Up 35° ± 2° Down (Elevator Neutral) Rudder Left: 25° ± 2° Right: 30° ± 2° Manufacturer's Serial Numbers 003 and up. Data pertinent to all models Empty Weight C.G. Range None. Equipment The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. In addition, the following is required. a. FAA approved Flight Manual dated May 21, 1975. b. See approved equipment list, Airplane Flight Manual. Certification basis FAR 21, effective February 1, 1965, including Amendments 1 through 37. FAR 23, effective February 1, 1965, including Amendments 1 through 12. Date of application for Type Certificate, October 24, 1972. Production basis None. Prior to original certification of each aircraft, an FAA representative must perform a detailed inspection for workmanship, materials, and conformity with the approved technical data, and a check of the flight characteristics. Export eligibility Aircraft will be eligible for issuance of an export certificate of airworthiness subject to compliance with Federal Aviation Regulation Part 21, Subpart L, Section 21.321 through 21.339. Special requirements of specific foreign countries are contained in Advisory Circular 21-2B. NOTE 1. Current weight and balance report, including list of equipment included in certificated empty weight and loading instructions, must be provided for each aircraft at the time of original certification. The empty weight and the corresponding center of gravity location must include the following unusable fuel: 13.2 pounds at (+23.0) NOTE 2. All placards required in the approved Airplane Flight Manual must be installed in the appropr iate locations. In addition,those placards not in the AFM but approved during type certification, are listed in the Maintenance Manual along with their location. ...END...