TCDS A65EU

Page No. 1 2 3 Rev. No. 3 2 3 DEPARTMENT OF TRANSPORTATION FEDERAL AVIATION ADMINISTRATION A65EU Revision 3 SME Aero, Inc MD3-160 March 27, 1996 TYPE CERTIFICATE DATA SHEET NO. A65EU This data sheet, which is part of Type Certificate No. A65EU prescribes conditions and limitations under which the product for which the Type Certificate was issued meets the airworthiness requirements of the Federal Aviation Regulations (FAR). Type Certificate Holder SME Aero, Inc. 3226 Capital Circle Tallahassee, Florida I - Model Swiss Trainer MD3-160, Utility and aerobatic aircraft certified by the Swiss Federal Office for Civil Aviation on 22nd January, 1961 Engine Avco Lycoming 0-320-D2A Fuel AVGAS, 100 & 100 LL Octanes Engine Limits Normal rated power Full throttle RPM 160 HP 117.7 KW 2700 Propeller and Propeller Limits McCauley 1-C172 AGM 7462 Weight 14.9kg 32.8lb Diameter 1.88m 74.0 in Static RPM at permissible throttle setting, not over 2400, not under 2250 Sensenich 74 DM6S8-0-62 Weight 14.7kg 32.4lb Diameter 1.88m 74.0 in Propeller Spinner Airspeed Limits Mt-Propeller P/N 3.03.15.13.31 VD = Maximum design dive speed VNE = Never exceed speed VC = Crusing speed VA = Maneuvering speed VFE = Maximum flap extended speed A65EU Page 2 Airspeed Limits (Continued VD VNE VC VA VFE Flight Load Factor Limits Max Positive Max Negative Utility Category (IAS) MPH/Kts 201/175 182/158 142/123 127/110 104/90 Utility Category +4.4g -2.2 Acrobatic Category (IAS) MPH/kts 226/196 201/175 159/138 139/121 104/90 Acrobatic Category +6g -3g C. G. Range Most forward C.G 11.81 in (300 mm) aft datum at 1790 lb (812 kg) 13.82 in (351 mm) aft of datum at 2028 lb (920 kg) Between the given values linear variation. Most rearward C.G. 14.76 in (375mm) afta of datum. Empty Weight C.G. Range See Flight Manual, Section 6: Weight & Balance Datum Wing Leading Edge. Leveling Means Canopy rails. Maximum Weight Maximum Take-Off Weight TOW Maximum Landing Weight MLW Minimum Crew Utility Category Aerobatic Category 2028 lb (920 kg) 1852 lb (40 kg) 1964 lb (891 kg) 1852 lb (840 kg) 1 pilot Number of Seats 2 (side by side) 7.6 in (193.4 mm) aft of datum. Maximum Luggage 110 lb (50kg) 38.6 in (980 mm)aft of datum Fuel Quantity Total Usable Arm 39.1 US Gal 38.0 US Gal 30.9 in aft of datum (148 lt) (144 lt) (785 mm) Page 3 A65EU Oil Quantity Total Arm 8 Quarts 39.8 in forward of datum (7.6 lt) (1011 mm) Control Surface Deflection (measured from neutral): Trim Tabs Balance Tabs Flaps Take-Off 15o +/2o Landing 48o+/-2o Ailerons Up 30 o +/-2o down 20o +/-2o Elevator Up 24 o +/-2o down 18o +/-2o Rudder left 32 o +/-2o right 32o +/2o Aileron left up 18o +/-2o down 18o +/-2o Elevator up 18 o +/-2o down 18o +/-2o Rudder left 7 o +/-1o Aileron right left at 0o trim, up 27o down 27o, +/-2o right at 0o trim, up 27o down 27o, +/-2o Rudder left at 0 o trim right 54o+/-2o right at 0 o trim left 40o +/-2o Nose Wheel Steering Left 30o right 44 o Serial Nos. Eligible S/N 003 to 005. Certification Basic 14 CFR Part 21.29, dated June 30th, 1988, utility and aerobatic category. (14 CFR Part 23, dated June 30th, 1988, utility and aerobatic category including amendments 23-1 to 23-35) Equipment NOTES Note 1. Note 2. The basic required equipment as prescribed in the applicable airworthiness regulations (see Certification Basis) must be installed in the aircraft for certification. Exhaust system installation of Either: a) Long exhaust system (MM 78-00-00) b) Short exhaust system (MM 78-00-00) in combination with the ventral fin P/N 0.03.12.59.52 on underside of rear fuselage. Current weight and balance data together with a 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. The placards listed in Section 2 of the Swiss FOCA - approved Airplane Flight Manual MD3-160 must be displayed. -END-